Composite materials comprising epoxy resin matrix and carbon fibers

ABSTRACT

This invention is directed to strongly bonded composite materials and a process for preparing the same, such materials comprising (1) a resinous matrix containing (2) carbon fibers having a Young&#39;&#39;s modulus parallel to the fiber axis of at least about 12 X 106 pounds per square inch and having a substantially continuous coating of amorphous carbon applied to the surface of such fibers prior to admixture with the resin matrix.

Unite States Patent Byrne et a1.

[ Dec. 10, 1974 COMPOSITE MATERIALS COMPRISING EPOXY RESIN MATRIX AND CARBON FIBERS Inventors:

Assignee:

Filed:

Appl. No.:

us. or. 117/161 ZB, 8/1156, 117/46 cc, 117/46 CB, 117/226, 117/228, 117/72,

264/29, 423/447 Int. Cl B4411 1/09 lField of Search 117/46 cc, 46 CB, 226, 117/228, 161 ZB; 423/447; 8/115.6; 264/29 Joseph B. Byrne, Antioch, Ca1if.; Harvey D. Ledbetter, Midland, Mich.

The Dow Chemical Company, Midland, Mich.

Mar. 10, 1972 References Cited UNITED STATES PATENTS Rivington 117/46 CC 3,367,812 2/1968 Watts 117/46 CC 3,395,970 8/1968 Machell..

3,519,604 7/1970 Maurer 117/161 ZB 3,530,093 9/1970 Maurer 117/161 ZB 3,705,236 12/1972 lshikowa et a1 423/447 Primary Examiner-William D. Martin Assistant Examiner.lanyce A. Ben Attorney, Agent, or Firm--Ronald G. Brookens [57] ABSTRACT 2 Claims, No Drawings COMPOSITE MATERIALS COMPRISING EPOXY RESIN MATRIX AND CAON FIBERS BACKGROUND OF THE INVENTION Carbon fibers having a Youngs modulus parallel to the fiber axis of at least about 12 X pounds per square inch are weakly bonded at the surface with resinous materials such as epoxy resins. Because of this, resin composites containing such fibers fail prematurely when subjected to applied force. Failure occurs in shear due to debonding of resin from the fiber surface. Composites containing relatively low modulus amorphous type carbon fibers, however, have higher values of interlaminar shear strength because of superior interfacial bonding.

The greater bonding ability of low modulus carbon fibers is believed to be due to the isotropic character of their surfaces. Fundamental structural units of these carbons are small and have a layered structure similar to that of graphite, but to a major extent are randomly disposed relative to each other. For these reasons a large proportion of the fiber surface will consist of exposed layer edges of the fundamental particles uniformly distributed over the surface. Exposed edges are believed to be highly reactive, may possess polar adducts, and may even bond chemically with epoxyresms.

Higher modulus carbon fibers are more ordered due to the occurrence of particle growth, partial graphitization, and orientation of crystallites during manufacture. The surface is generally anisotropic, consisting of relatively large areas of exposed crystallite basal planes and lessened exposure of edges. Crystallite basal planes are believed to have low reactivity and to bond only poorly with resins.

Prior efforts to improve the shear properties of carbon fibers have involved the following approaches:

A. Coat the fiber surface with a silane or amine type coupling agent.

(Steingiser, Samuel, and RA. Cass; Graphite Fiber Reinforced Composites. Technical Report AFML- TR-68-357, Part I, November, 1968;

Herrick, John W.; Resin-Fiber Interactions in Graphite Fiber Epoxy Composites, 23rd Annual Technical Conference, 1968 Reinforced Plastics/Composites Division, The Society of The Plastics Industry, lnc., Section 16A, pp. l-8;

Prosen, S. P., J. V. Duffy, P. W. Erickson and M. A. Kinna; 21st Annual Technical Conference, 1966 Reinforced Plastics/Composites Division, The Society of The Plastics Industry, lnc., Section D; and Harris, 8., D. W. P. Beaumont, A. Rosen; J. of Materials Science, 4, 432-438 (1969)).

B. Grow silicon carbide whiskers on the fiber surface in a direction perpendicular to the fiber axis.

(Simon, R. A., and S. P. Prosen, Graphite Fiber Composites; Shear Strength and Other Properties, 23rd Annual Technical Conference, 1968 Reinforced Plastics Composites Division, The Society of The Plastics Industry, lnc., Section 168, pp. l-lO).

C. Treat the fiber at boiling temperature with an aqueous solution of an oxidizing agent.

(Prosen, S. P., J. V. Duffy, P. W. Erickson and M. A. Kinna; 21st Annual Technical Conference, 1966 Reinforced Plastics/Composites Division, The Society of ThePlastics Industry, lnc., Section D).

D. Treat the fibers in air for a prolonged period at temperatures up to 1,000C.

(US. Pat. No. 3,476,703).

E. Contact heated carbon filament with a BCl toluene mixture in the vapor phase.

(Quackenbush, N. E., et al., Development of Surface Treatments for High-Modulus Graphite Fibers,

Aeronutronic Publications on Contract No. N000l9- -C-030l Dept. of Navy, Naval Air Systems Command, September, 1970).

F. Deposit a metal salt or metal complex from solution and decompose at high temperature, and

G. Form a coating of carbon on the fiber surface.

(Larsen, J. V., Surface Treatments and Their Effects on Grapite Fibers." Paper presented at 16lst Meeting, A.C.S., Los Angeles, March 29-May 2, I971 Preprints, page 428, Division of Organic Coatings and Plastics Chemistry).

Method A, treatment with coupling agents, has generally not been successful. Growth of SiC whiskers on carbon fibers in Method B is accomplished by exposing the fibers to a source of silicon and carbon at 1,100 l650C. Treated fibers resemble a foxtail, the whiskers protruding from the fibers in all directions around the fiber. Considerable care must be exercised during the whiskerizing process to avoid degrading fiber tensile strength. The presence of whiskers attached to the surface also precludes close approach of fibers to each other. The high fiber concentrations attainable in a composite with nonwhiskered fibers is not possible with whiskerized fibers.

Oxidizing agents used in Method C have included nitric acid, sodium hypochlorite, and acidicpotassium permanganate. Significant surface activation is obtained with nitric acid; however, reaction times with refluxing nitric acid ranging from 24 to 48 hours arenecessary.

In Method D, carbon fibers were [heated in air at temperatures of 550C. and 600C. for periods ranging up to 4 hours. Fiber weight losses as high as 3.56 percent result with fibers having a pitted surface obtained simultaneously with this weight loss.

In Method E, vapor phase treatment with BCI and toluene, yields fibers with improved shear strength compared to untreated fibers, but with the deposition of both boron and carbon on the fiber surface.

In Method F, ferric chloride, ferrocene, and a chromium complex was deposited on carbon fibers and then decomposed at high temperatures. Improved fiber shear strength was achieved in each case, but fiber tensile strength decreased after treatment with ferric chloride.

The Method G, deposition of carbon on the fiber surface, is similar to the present invention. The investigator in this case, J. V. Larsen, used two methods to deposit carbon on the fiber surface. In one method, he heated carbon fibers by electrical resistance to 1,200C., and then contacted the hot fibers with a mixture of methane and nitrogen. The methane decomposed on the hot fibers forming a carbon coating on their surfaces. Larsen discloses that. a two-fold increase in shear strength over untreated fibers was obtained with this treatment. Some loss of fiber tensile strength was also observed.

In the second method, carbon fibers are impregnated with a solution of a phenylated polyquinoxaline. The fibers were dried and then brought to an unspecified high temperature up to 1,600C. by electrical resistance heating. It is stated that composite shear strength of these fibers improved by a factor of 2.7 over untreated fibers.

Coating carbon fibers with carbon by the pyrolysis of methane is also described in British Pat. No. 1,122,645 where the coating is formed between 1,800C. and 2,300C. X-ray diffraction patterns of pyrolytic carbons deposited from methane at temperatures of 1,600C., 1,850C. and 2,150C. (as reported by Blackman, Saunders and Ubbelohde in Proc. Royal 800., 264A, 19 (1961)) show the progression of crystalline order and preferred orientation in these carbons with deposition temperature.

Carbon deposited at 1,600C. is essentially isotropic, although a slight degree of preferred orientation is detected in the X-ray patterns. The 1,850C. carbon shows marked anisotropy with some misorientation of crystallite basal planes. Carbons obtained at 2,150C. show preferred orientation of crystallites and an advanced degree of graphitization. Thus, crystallite orientation and the process of graphitization is beginning at deposition temperatures greater than 1,600C. Density and interlayer spacing data from the same reference indicate such changes in structure beginning at 1,7001,750C. Marked changes in properties occur at an apparent critical deposition temperature of 1,900C.

SUMMARY OF THE INVENTION The present invention is directed to a means of obtaining strongly bonded composite materials by a process comprising preparation of a resinous matrix containing carbon fibers having a Youngs modulus parallel to the fiber axis of at least about 12 X pounds per square inch and having a substantially continuous coating of amorphous carbon (as determined by electron diffraction) applied to the surface of such fiber prior to admixture with the resin matrix. More specifically, it comprises deposition on such fibers of a thermally carbonizable organic precursor material followed by pyrolyzing such precursor at temperatures below 1,200C., and preferably wherein such pyrolysis takes place in a nitrogen atmosphere containing from about 900 ppm to about 3,200 ppm of oxygen.

It has been discovered, which discovery forms part of the present invention, that utilization of such process provides improved interfacial shear strength in a resin matrix, e.g., an epoxy resin, particularly when the amorphous carbon coating is derived from materials such as polyvinylidene chloride, polyacrylonitrile or polyvinyl chloride. It has also been discovered that the amorphous coating produced on the carbon fibers utilized in the present invention has significant utility as a sizing agent, i.e., carbon fiber tow coated with amorphous carbon has a much smaller bulk diameter than uncoated tow. This occurs because fibers in the tow are initially drawn closely together through the surface tension of the coating solution. Fibers are held in close proximity by subsequent formation of occasional carbon bridges and areas of adhesion between individual fibers. Because of the close proximity of fibers and the bridges between them, tows containing carbon coated fibers are stiffer than tows with uncoated fibers. The degree of stiffness can be controlled since stiffness depends on the amount of carbon deposited. Tow containing carbon coated fibers are also more easily handled and suffers less snagging and snarling of fibers than tow with uncoated fibers.

The amorphous carbon coating, as described herein, is one in which the crystallite basal planes of the coating must be substantially random with respect to the surface. An amorphous coating will shown no orientation in an electron diffraction pattern using 50KV electrons when deposited to a uniform thickness of A or more. Thin amorphous coatings may be difficult to characterize because of reflections from fundamental particles of the underlying carbon fiber. For this reason the test for amorphous character of the carbon coating requires a coating sufficiently thick to obscure reflections from the underlying structure.

DESCRIPTION OF PREFERRED EMBODIMENTS The carbon fibers which are utilizable in the present invention may be any such fiber having a Youngs modulus parallel to the fiber axis of at least about 12 X 10 pounds per square inch. Exemplary of polyacrylonitrile fibers are those disclosed in British Pat. Nos. 1,170,591 and US. Pat. No. 3,412,062. Carbon fibers derived from rayon, pitch (either from hydrocarbon or wood), phenolic resins, epoxy resins, rayon and saran may also be used.

The carbonizable organic precursor materials contemplated by the present invention include any material capable of forming solutions in a volatilizable solvent and which form an amorphous carbon coating on the carbon fibers when pyrolyzed at temperatures below 1,200C. Exemplary of preferred carbonizable materials are polyvinylidene chloride, polyacrylonitrile and polyvinylchloride, asphalt, cured epoxy resins, petroleum pitch, phenolic resins, polyimide resins and polybenzimidazol resins, among others. Preferred volatilizable solvents are hexamethylphosphoramide (when using polyvinylidene chloride as the carbonizable organic precursor); dimethylformamide (when using polyacrylonitrile as the organic precursor) and methyl ethyl ketone (when using polyvinylchloride as the organic precursor).

Important process variables of this invention include: molecular weights of the carbonizable organic precursor; concentration of precursor in the solvent used, maximum heating temperature; and dwell time at maximum temperature.

Molecular weight of precursor and its concentration in the solvent are important variables in that they affect the amount of precursor material picked up by the carbon fiber strand. This in turn affects stiffness of the strand and associated strand processibility. Carbon fiber tow has been satisfactorily coated with carbon after impregnation with a solution containing 1.25 gpl polyvinylidene chloride in hexamethylphosphoramide. Coated tow with satisfactory properties may be obtained by impregnating with a solution containing as low as 0.5 gpl precursor. Generally, precursor concentrations in the impregnating solution ranging from 0.5 to 50 gpl may be used. This will give carbon coatings on the carbon fibers of a few A to 300A or more thickness. It is possible to modify the process such that coatings up to 10,000A or more are deposited. Preferred precursor concentrations are 1 gpl to 10 gpl with subsequent coatings, 20A to 200A thickness.

The range of precursor concentration may have to be modified with different precursor-solvent systems. The

optimum precursor concentration can easily be determined with a few experiments.

It has also been discovered, which discovery represents part of the present invention, that improved results are obtained by pyrolyzing the carbonizable organic precursor in a nitrogen or other inert atmosphere containing relatively small amounts of oxygen. In this regard, an oxygen concentration in the nitrogen atmosphere of approximately 900 ppm is necessary to obtain activated fibers having optimum shear properties. Such fibers are also obtained even when activated at oxygen concentrations as high as 3,200 ppm. However, some loss of fiber tensile strength occurs at this oxygen concentration. It is thus preferable to operate with an oxygen concentration of about 1,000 ppm.

A flow of nitrogen is maintained into the hot tube through which the carbon fibers are drawn for surface activation. Since the tube is partially open at both ends, the nitrogen flow must be sufficiently high to prevent back diffusion of air into the tube. Flow rates of about 2,000 ml/min. are generally sufficient. This represents a tube volume turnover of 7 /2 times per minute.

The temperatures used for pyrolyzation of the carbonizable organic precursors are those temperatures less than 1200C. and preferably temperatures between about 900C. and l,100C.

Fiber dwell time at maximum temperature was usually adjusted to approximately minutes. Longer dwell times up to 30 minutes did not significantly alter fiber shear properties. The shortest possible dwell time may be dependent on prior heating temperatures.

The experiments specifically set forth hereinafter were carried out at final carbonization temperatures of from 915C. to 950C. (Temperature of the last heater in the heating system). Fiber dwell time at these temperatures ranged from 13 to 21 minutes. These times are probably longer than necessary for the carbonization temperatures used. Shortest possible time will be process dependent, i.e., it will depend on the temperatures at which preceding heaters in the carbonization equipment are held. It is believed that optimum dwell time at final temperature of 915C. to 950C. may be as low as 1 to 5 minutes.

The final carbonization temperature may be reduced to approximately 500C. using a polyvinylidene chloride precursor. (See Example I).

' Carbonization of polyacrylonitrile in the neighborhood of 700C. (in the presence of oxygen) is nearly complete, provided that the polymer is preheated in an oxidizing atmosphere. Optimum fiber dwell time at lower carbonization temperatures will of course be longer. Optimum dwell time can be easily determined experimentally.

Carbon fibers coated with amorphous carbon are advantageously used with epoxy resin or other resins to improve mechanical properties of the resin. The amorphous carbon coating will improve handling characteristics of the fiber, and will protect them from damage through snagging with equipment or with other-fibers.

The following nonlimiting examples are set forth to more specifically describe and illustrate the present invention:

Materials used in the following examples were as follows: carbon fibers, polyvinylidene chloride, hexamethylphosphoramide, polyacrylonitrile, dimethylformamide, polyvinylchloride, methyl ethyl ketone and ni- Ultimate Filament Average Tensile Mod. of Fiber Diameter Density Strength, Elast, Type Microns Lbs/Cu. Ft. X 10 psi X 10 psi HM 83:35 0.0693 250-350 50-60 HT 8.6:45 0.0635 300-400 32-40 These fibers were manufactured from a polyacrylonitrile starting material. HM type fibers were graphitized at 2,300C. HT type fibers were processed to a maximum temperature of 1,500C.

Hexamethylphosphoramide, used as a solvent for polyvinylidene chloride, was a commercial product and was used as supplied.

Polyacrylonitrile molecular weight from viscosity measurement was 312,000. Reagent grade dimethylformamide was used as solvent for polyacrylonitrile.

Nitrogen was pre-purified grade guaranteed by the supplier to contain less than 5 ppm 0 and to consist of 99.99% N The epoxy resin system used for the preparation of composites was ERL 2,256 with ZZL 0,820 hardener. Resin to hardener ratio was 100/37 parts by weight. Epoxy composites stood overnight at ambient temperature. They were cured 2 hours at 82C. and 2 hours at 148C.

ERL 2256 is a mixture containing 62.5 percent diglycidyl ether of Bisphenol A and 37.5 percent bis(2,3-epoxycyclopentyl) ether. ZZL 0820 is an eutectic mixture of m-phenylenediamine and methylenedianiline. 1

All composites tested were fabricated with the epoxy resin system described above.

EXAMPLEv 1 Temp. C. Time, Minutes Atmosphere 139 Air l 79-200 60 N 430-450 61 N 530-550 78 Six test strips each containing a single length of treated tow encapsulated in an excess of epoxy resin were fabricated. Dimensions of the test strip were 0.015 X 0.5 X 5 inches. They were fabricated between two sheets of polyethyleneterephthalate with suitable spacers to control width and thickness. The cured test strips were broken in tension with an Instron Testing Machine at a crosshead speedof 0.2 inch/minute. Fi-

bers protruding from the broken end of a test strip were brought into focus at 400x with an optical microscope. The protruding lengths of 130-160 fibers from ten broken ends were measured at random by means of a calibrated scale in the eyepiece. A total of 1,426 measurements were made. The average protruding or pullout length from these measurements was 19 X 10 inches. lnterfacial shear strength was calculated from the equation:

'r shear strength; (1 fiber diameter; fiber tensile strength; 1 average fiber pull-out length.

Interfacial shear strength determined from these measurements was 1 1,560 psi. Interfacial shear strength with untreated fibers determined by the same method was 7,580 psi.

EXAMPLE ll Graphitized carbon fibers (HM type) were processed in a separate experiment. This was accomplished by passing the carbon fiber consecutively from a fiber feed roll (A), over a pigtail fiber guide (B), into an impregnating bath (C), then between a pair of infra-red lamps (D), between cylindrical heating units (1), over guide roll (F), between a second pair of cylindrical heating units (2), over guide rolls (G), (H) and (I), between other cylindrical heating units (3), (4) and (5) (arranged in series), under a nitrogen inlet tube (J) and onto a take-up roll (K). In such process, carbon fiber is fed through a solution of carbonizable organic precursor at (C), the solvent is evaporated in air by passage of the fiber through the infra-red lamps (D) and heating units 1 and 2. The fiber then travels through the heating units (3), (4) and (5) where carbonization of the organic precursor occurs.

Three runs were made wherein the concentrations of polyvinylidene chloride in hexamethylphosphoramide at (C) were respectively 1.25 gpl, 5 gpl, and gpl. Fiber travel rate was held between 7.6 and 9.4 ft./hr. Prepurified nitrogen was fed into the system. Temperatures of the ovens were as follows: 1, 67-72C.; 2, l45-154C.; 3, 180C.; 4, 400C; 5, 935-940C.

The tow obtained was in all cases of reduced bulk diameter and stiffer than the original untreated tow. Visible comparison of the tows shows that tow stiffness and reduction of bulk diameter becomes greater as one increases the concentration of polyvinylidene chloride in the impregnating solution. The tow obtained could also in all cases be freely handled, and was less subject to snagging and snarling than untreated tow.

Epoxy resin composites were fabricated with fibers from each of the runs, and also with the original untreated fibers. lnterlaminar shear strength of each composite was measured by the short beam method. (See attached procedure). The results from these measurements at 60%V graphitized fibers are reported below in Table l. Tensile strength of the fibers is also reported (1) Interlaminar Shear Strength (1.L.S.S.)

A composite test bar is fabricated by laying resin impregnated tow into a rectangular, open-ended mold. Excess resin is forced out through the open ends by application of pressure to a rectangular piston-like bar inserted in the mold. Thickness of the test bar is set by shoulders on the pressure application bar which act as stops to movement. Dimensions of the test bar were 0.13 X 0.25 X 7 inches. The bar was cut into test pieces, 0.635 inch in length, for measurement of interlaminar shear strength. Test method used is ASTM-D 2344-67. Span to depth ratio was slightly less than 4:1.

The bars were fabricated to contain 60 percent by volume parallel fibers. Actual fiber content was determined analytically by digestion of a portion of the bar with nitric acid. Density was calculated from the dimensions of each test bar and its mass in air.

(2) Measurement of Fiber Tensile Strength The method used is a single fiber evaluation method. It is described in the following Air Force Report.

Evaluation Technique for Fibers and Yarns. Used by Fibrous Materials Branch, Non-metallic Materials Branch, Air Force Materials Laboratory. AFML- TR-67-159, Fibrous Materials Branch, September, 1967.

The data show that epoxy resin composites containing carbon coated graphitic fibers have improved interlaminar shear strength over a composite containing uncoated fibers. The improvement with carbon coated fibers holds for all concentrations listed of polyvinylidene chloride in the impregnating solution. The data also show an optimum concentration of polyvinylidene chloride near 5 gpl.

Average tensile strength of the carbon coated fibers of this example was 314,000 psi. Average tensile strength of the same fibers prior to coating was 269,000

EXAMPLE lll Graphitized carbon fibers (HM type) were used to fabricate epoxy resin composites containing approximately 60%V to 71%V carbon fibers. Interlaminar shear strength of these composites was measured by the short beam method. Results of the measurements are listed in Table 11 below:

TABLE 11 Carbon Fibers 1.L.S.S

%V psi posites, measured by the short beam method, are listed in Table III below.

The above data illustrate that epoxy resin composites fabricated with carbon coated fibers are superior in interlaminar shear strength, to similar composites fabricated with corresponding noncoated fibers. lnterlaminar shear strength of carbon fiber epoxy resin composites are thus more efficiently retained at high fiber concentrations with use of carbon coated fibers than with uncoated fibers.

Average strength of fibers coated with carbon by the process described was 251,000 psi. Average strength of the same fibers prior to coating was 231,000 psi.

EXAMPLE IV Graphitized carbon fibers (HM type) were impregnated with a solution of polyvinylchloride in methyl ethyl ketone, and processed through a modification of theequipment described in Example 11.

Two experiments were made. In one experiment, the concentration of polyvinylchloride in the impregnating solution was 3.5 gpl, and in the second, 10 gpl. Nitrogen was fed into the system at a rate of 2,000 ml/min. Fiber travel rate was 8.1 ft./hr. Temperatures of the heating units numbered in the sketch were as follows: 3, 220C; 4, 460C; 5, 935-940C. The tow obtained after this treatment was similar to that described in Example ll.

Epoxy resin composites were fabricated with fibers from each of the runs, and also with the original untreated fibers. Interlaminar shear strength of each composite was measured by the short beam method. Tensile strength of the treated and untreated fibers was also measured. Results from these measurements are presented in Table IV. lnterlaminar shear strength results are normalized to 60 percent by volume graphitized fibers.

TABLE IV PVC COI'IC. I.L.S.S. Fiber Tensile Strength gpl psi psi X 10'' The data show an improvement in interlaminar shear strength, and also in fiber tensile strength after coating fibers with carbon derived from polyvinylchloride.

EXAMPLE V tube heated by the high temperature ovens 3, 4 and 5. They were then collected on a motordriven reel. Temperatures of the heating units were varied as follows:

TABLE V Heating Unit Temp. Range, 'C.

Nitrogen was fed at 2000 ml/min. intothe Vycor tube at (J). Air was simultaneously introduced into the nitrogen stream at a fixed rate. Analysis of the nitrogen discharged from the tube showed an oxygencontent of 1,000 ppm on a volume basis.

A number of runs were made wherein the temperature of Ovens 1 through 4 were in all cases within. the range shown in Table V. For each run the temperature of Oven 5 was held at some fixed temperature within the range shown in Table V. For this series of runs the concentration of PVDC in the I-lMPA solution used was 10 gpl.

Epoxy resin composites were fabricated with fibers from each of the runs, and also with the original untreated fibers. Interlaminar shear strength of each composite was measured by the short beam method. The results from these measurements at 60 percent by volume of graphitized fibers are reported below in Table I1. Tensile strength of the fibers are also reported in Table VI.

The data presented in Table VI show that fibers treated as described have improved tensile strength and substantially improved bonding with epoxy resins.

EXAMPLE Vl A number of runs were made wherein carbon fibers (HT type) were drawn through the equipment described in Example 11. In these runs the oxygen concentration in the nitrogen atmosphere was varied from 296 ppm (volume bases) to 3,140 ppm. In all of the runs, concentration of polyvinylidene chloride in hexamethylphosphoramide was 10 gpl. Temperature of Oven 5 was held at 920C. Tensile strength of treated fibers and also interlaminar shear strength of epoxy resin composites fabricated with these fibers are listed in Table VII, together with the concentration of oxygen maintained during processing. Tensile strength and interlaminar shear strength obtained with untreated fibers are also included.

TABLE VII Concent. Fiber Tensile lnterlaminar ppm, V Strength Shear Strength psi psi Untreated 275,000 4,760 296 267,000 5,920 518 366,000 10,550 1,065 282,000 13,830 1,485 236,000 14,100 1,770 266,000 13,410 2,090 246,000 13,390 2,410 285,000 13,720 2,900 244,000 13,000 3,140 227,000 14,050

The data above illustrate the relatively small changes in fiber tensile strength which occur with increase of oxygen concentration after treatment of the fiber by the process described. It also demonstrates the improvement in composite interlaminar shear strength obtained with carbon fibers treated at various oxygen concentration levels.

EXAMPLE VII Carbon fibers (HT type) were impregnated with a solution containing 5 gpl polyacrylonitrile in dimethylformamide, and processed through a modification of the equipment described in Example 11. In the modified equipment, the impregnating solution was moved from point (C) to a position near point (I). The fiber feed reel was moved from point (A) to point (H). Heaters 1 and 2 were not used. Nitrogen containing 1080 ppm oxygen was fed into the system at a rate of 2000 ml/min. Fiber travel rate was 8.7 ft./hr. Temperatures of the heating units were as follows: 3, 222C; 4, 460C; 5, 945C.

An epoxy resin composite was fabricated with the fibers treated as described, and also with the original untreated fibers. lnterlaminar shear strength of each composite was measured by the short beam method. lnterlaminar shear strength at 60% fibers by volume of the composite fabricated with the treated fibers was 13,250 psi, and that of the composite fabricated with the original untreated fibers was 3,410 psi.

EXAMPLE VIII Carbon fibers (HT type) were impregnated with a solution of asphalt in p-xylene, and processed through a modification of the equipment described in Example 11.

The asphalt used was industrial grade material. Its softening point was within the range 185F. to 200F. Asphalt concentration in the p-xylene impregnating solution was 20 gpl. Nitrogen was fed into the system at ,a rate of 2,000 ml/min. Fiber travel rate was ft./hr. Temperatures of the heating units were as follows: 3, 158C.; 4, 45 8C.; 5, 940C. The tow obtained after this treatment was similar to that described in Example II.

Epoxy resin composites were fabricated with the carbon coated fibers obtained as described above, and also with the original untreated fibers. lnterlaminar shear strength of each composite was measured by the short beam method. Tensile strength of the treated and untreated fibers was also measured. lnterlaminar shear strength of the composite containing 60% by volume of untreated fibers was 3,410 psi. lnterlaminar shear strength of the corresponding composite containing the carbon coated fibers was 5,120 psi. Tensile strengths of untreated and carbon coated fibers were respectively 265,000 psi and 336,000 psi.

EXAMPLE IX Carbon fibers (HM type) were impregnated with a solution of asphalt in p-xylene, and processed through a modification of the equipment described in Example II.

The asphalt used was industrial grade material. Its softening point ranged from 185F. to 200F. Asphalt concentration in the p-xylene impregnating solution was 2.5 gpl. Nitrogen was fed into the system at a rate of 2,000 ml/min. Fiber travel rate was 8.9 ft./hr. Temperatures of the heating units numbered in the sketch were as follows: 3, 167C; 4, 447C.; 5, 940C. The tow obtained after this treatment was similar to that described in Example 11.

Epoxy resin composites were fabricated with the carbon coated fibers obtained as described above, and also with the original untreated fibers. lnterlaminar shear strength of each composite was measured by the short beam method. Tensile strength of the treated and untreated fibers was also measured. lnterlaminar shear strength of the composite containing 60 percent by volume of untreated fibers was 10,350 psi. lnterlaminar shear strength of the corresponding composite containing the carbon coated fibers was 11,360 psi. Tensile strengths of untreated and carbon coated fibers were respectively 287,000 psi and 280,000 psi.

EXAMPLE X Carbon fibers (HT type) were impregnated with a methyl ethyl ketone solution containing a mixture of epoxy resins and amine hardener. The epoxy resin mixture was composed of 62.5 percent diglycidyl ether of Bisphenol A and 37.5 percent bis(2,3-epoxycyclopentyl) ether. The amine hardener was an eutectic mixture of m-phenylenediamine and methylenedianiline. Epoxy resin and hardener were mixed at a ratio of /37 parts by weight before dissolving in methyl ethyl ketone. Concentration of the resin-hardener mixture was 20 gpl. The impregnated fibers were processed through the equipment described in Example 11.

Nitrogen was fed into the system at a rate of 2000 ml/min. Fiber travel rate was 12.4 ft./hr. Temperatures of the heating units were as follows: 1, 97C.; 2, 92C.; 3, 222C; 4, 460C; 5, 940C. The tow obtained after this treatment was similar to that described in Example 11.

Epoxy resin composites were fabricated with the carbon coated fibers obtained as described above, and also with the original untreated fibers. lnterlaminar shear strength of each composite was measured by the short beam method. Tensile strength of the treated and untreated fibers was also measured. lnterlaminar shear strengths of composites containing 60 percent by volume of untreated and carbon coated fibers were respectively 3,410 psi and 5,020 psi. Tensile strengths of untreated and carbon coated fibers were respectively 265,000 psi and 316,000 psi.

What is claimed is:

1. Carbon fiber having improved bonding to an epoxy resin matrix said fiber having a Youngs modulus parallel to the fiber axis of at least about 12 X 10 pounds per square inch and the surface of said fiber being coated with an essentially continuous coating of amor- M inch and the surface of said fiber being coated with an essentially continuous coating of amorphous carbon, said coating having a thickness of from about 20 A to about 200 A and being obtained by deposition of a thermally carbonizable organic precursor onto the carbon fiber said organic precursor being thermally carbonized to amorphous form at temperatures less than 1,200c. 

1. CARBON FIBER HAVING IMPROVED BONDING TO AN EPOXY RESIN MATRIX SAID FIBER HAVING A YOUNG''S MODULUS PARALLEL TO THE FIBER AXIS OF AT LEAST ABOUT 12X10**6 POUNDS PER SQUARE INCH AND THE SURFACE OF SAID FIBER BEING COATED WITH AN ESSENTIALLY CONTINUOUS COATING OF ARMORPHOUS CARBON, SAID COATING HAVING A THICKNESS OF FROM ABOUT 20 A TO ABOUT 200 A AND BEING OBTAINED BY DEPOSITION OF A THERMALLY CARBONIZABLE ORGANIC PRESURSOR ONTO THE CARBON FIBER SAID ORGANIC PRECURSOR BEING THERMALLY CARBONIZED TO AMORPHOUS FORM AT TEMPERATURES LESS THAN 1,200*C.
 2. A composite material comprising an epoxy resin matrix containing a plurality of flexible carbon fibers said fibers having a Young''s modulus parallel to the fiber axis of at least about 12 X 106 pounds per square inch and the surface of said fiber being coated with an essentially continuous coating of amorphous carbon, said coating having a thickness of from about 20 A to about 200 A and being obtained by deposition of a thermally carbonizable organic precursor onto the carbon fiber said organic precursor being thermally carbonized to amorphous form at temperatures less than 1,200*C. 